Aerodynamic surface of an aircraft

Abstract

An aerodynamic surface of an aircraft comprises a main part having a leading and a trailing edges and having an airfoil section. The aerodynamic surface also having at least two vortex generators in the form of teeth having edges along the length thereof. The teeth are mounted on the leading edge of the main part so as to be capable of generating two vortex cores on one tooth. The edges of a tooth adjoin the leading edge of the main part of the aerodynamic surface. The radius of an edge of each tooth along the length of the vortex generator is five times less than the radius of the leading edge of the main part. The main part of the aerodynamic surface has a cambered airfoil section, wherein the teeth are mounted with a deflection towards the smallest degree of curvature of the airfoil section of the main part. The invention is intended for reducing an aerodynamic drag at low angles of attack while maintaining an increased load hearing capacity of the aerodynamic surface by generating vortex cores adjoining one of the sides thereof.

1 . An aerodynamic surface of an aircraft, comprising
 a main part having a leading edge and a trailing edge and having an airfoil section;   at least two vortex generators in the form of teeth having edges along the length thereof, wherein the teeth are mounted on the leading edge of the main part so as to be capable of generating two vortex cores on one tooth, the edges of a tooth adjoin the leading edge of the main part of the aerodynamic surface, and the radius of an edge of each tooth along the length of the vortex generator is at least five times less than the radius of the leading edge of the main part,   characterized in that the main part of the aerodynamic surface has a cambered airfoil section, and the teeth are mounted with a deflection towards the smallest degree of curvature of the airfoil section of the main part.   
     
     
         2 . The aerodynamic surface according to  claim 1 , characterized in that
 a ratio of the width of the tooth base to the height thereof is from 0.8 to 3;   a ratio of the width of the tooth base to the distance between the teeth is from 1.6 to 3.5; and   the height of the tooth is equal to 10-45% of a local chord of the main part of the aerodynamic surface.   
     
     
         3 . The aerodynamic surface according to  claim 1 , characterized in that the edges of the teeth are made sharpened by at least 50% of the length thereof. 
     
     
         4 . The aerodynamic surface according to  claim 1 , characterized in that the leading edge of the main part of the aerodynamic surface is made wavy;
 the teeth are disposed on the protrusions of the wavy surface of the leading edge; and   the maximum foil difference of the wavy surface is from one twentieth to one third of the distance between the teeth.   
     
     
         5 . The aerodynamic surface according to  claim 1 , characterized in that it further comprises at least one deflectable trailing edge assembly hingedly mounted on the trailing edge of the main part of the aerodynamic surface, and at least one of the teeth is configured to be deflected relative to the main part of the aerodynamic surface and is kinematically connected to the deflectable trailing edge assembly of the aerodynamic surface so as to be capable of being synchronously deflected relative to the main part of the aerodynamic surface, providing the creation of a total aerodynamic force or moment with the simultaneous aerodynamic compensation of a hinge moment of the movable trailing edge assembly owing to the hinge moment of said at least one of the teeth that is opposite in sign. 
     
     
         6 . The aerodynamic surface according to claim I, characterized in that the main part of the aerodynamic surface is made in the form of a leading and a trailing aerodynamic member mounted one after another, and the teeth are mounted between the leading and trailing aerodynamic members, forming trapezoidal windows tapering in the air flow direction so as to be capable of generating vortex cores adjoining the surface of the trailing aerodynamic member.